Due to successful noise reduction strategies concerning fan- and jet-noise in gas turbine configurations, the relevance of combustion noise is increasing. In order to distinguish between turbulent noise and combustion noise a model gas turbine combustor consisting of a swirl burner and an exit nozzle of Laval-shape is investigated. Because of the instationary character of the flow this configuration is analysed by means of Large Eddy Simulation (LES). Numerical results are first validated by comparison with experimental data. Then a numerical study of noise generated by turbulent flow instabilities is carried out. Providing an extensive temporal and spatial analysis of the isothermal flow length- and timescales as well as vorticitiy are investigated with regard to the formation of rotating flow-instabilities in the recirculating swirling flow. Subsequently a link to the acoustic perturbation equations (APE) is provided, from which the Lamb vector represents the essential noise sources. Therfore noise sources are identified and evaluated by means of LES based on the Lamb vector consideration. It results that the noise sources increase with an increasing swirl number.

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